A general aviation low-orbit satellite communication terminal

Abstract

The present invention provides a general aviation low-orbit satellite communication terminal, comprising a first welding plate, a square sleeve, a first screw and a square frame plate, wherein a plurality of first welding plates are respectively welded transversely to the lower ends of the left and right sides of four square sleeves, and a plurality of first screws are respectively penetrated and arranged at the upper ends of the plurality of first welding plates. This design enables the device to have a stable supporting function, and there is no need to fix the satellite communication terminal body on the outside, thereby solving the problem that the original satellite communication terminal is inconvenient to disassemble after installation, and improving the disassembly and assembly efficiency of the present invention. The square frame plate is welded in the middle of the annular side surface of the square support rod of the satellite communication terminal, and this design enables the device to have an auxiliary movement function, and is easy to use without manual transportation, thereby solving the problem that the original satellite communication terminal needs to be manually transported and transferred after disassembly, which is relatively inconvenient, and improving the convenience of use of the present invention. Compared with the prior art, the present invention has a reasonable structure and is easy to use.

Description

Technical Field

[0001] The invention discloses a general aviation low-orbit satellite communication terminal, belonging to the technical field of satellite communication equipment. Background Art

[0002] Low-orbit satellites are mainly used for military target detection and are also used for mobile phone communications. In the mobile satellite communication system, the user segment needs to access the mobile satellite communication network through the ground segment for mobile communications. The communication terminal representing the user segment can have different forms, such as handheld terminals, satellite communication terminals installed outside, or vehicle-mounted terminals. The user terminal is used to enable the terminal user to set and obtain the communication status and complete the communication by installing a wireless transceiver antenna.

[0003] Taking the satellite communication terminal installed on the ground as an example, its structure is fixed and it is inconvenient to disassemble after installation. Moreover, it needs to be manually moved after disassembly, which is quite inconvenient. Now there is an urgent need for a general aviation low-orbit satellite communication terminal to solve the above problems. Summary of the invention

[0004] In view of the shortcomings of the prior art, the object of the present invention is to provide a general aviation low-orbit satellite communication terminal to solve the problems raised in the above background technology.

[0005] In order to achieve the above-mentioned purpose, the present invention is realized by the following technical scheme: a general aviation low-orbit satellite communication terminal, comprising a satellite communication terminal body, a mobile component and an auxiliary support mechanism, wherein a square support rod of a satellite communication terminal is longitudinally installed on the back of the satellite communication terminal body, and the mobile component comprises a square frame plate, a mounting plate, a square sleeve, an electric telescopic rod, a limit ring, a moving wheel and a connecting angle plate, wherein the square frame plate is welded in the middle of the annular side of the square support rod of the satellite communication terminal, and the mounting plate and the square sleeve are arranged in four equal specifications, and the four square sleeves are respectively longitudinally welded to the lower ends of the four mounting plates, and the four mounting plates are installed around the lower end of the square frame plate at equal angles through a plurality of flanged nuts and a plurality of flanged bolts, and the auxiliary support mechanism comprises a first welding piece, a first screw, a threaded block, a metal tip, a second welding piece, an inclined leg, a second screw, a support bottom plate, a circular metal sheet and a circular rubber sheet, and the first welding piece, the first screw, the threaded block and the metal tip are arranged in multiple equal specifications, and the plurality of the first welding pieces are respectively transversely welded to the lower ends of the left and right sides of the four square sleeves, and the plurality of the first screws are respectively arranged through the first welding piece.

[0006] Furthermore, in the easy-to-move component, four electric telescopic rods, limiting rings and moving wheels are provided with equal specifications. The four electric telescopic rods and the four limiting rings are longitudinally fixed inside four square sleeves, and the four limiting rings are fixed on the lower ends of the four electric telescopic rods, respectively. The four moving wheels are located inside the four square sleeves, and are fixed on the lower ends of the four electric telescopic rods, respectively. A small battery is placed on the rear side of the upper end of the square frame plate, and the small battery is bidirectionally electrically connected to the four electric telescopic rods through wires.

[0007] Furthermore, there are multiple connecting angle plates of different specifications, and the multiple connecting angle plates are fixedly connected to the left and right sides of the four square sleeves by multiple mounting bolts, and the multiple connecting angle plates are fixedly connected to the four side surfaces of the square support rod of the satellite communication terminal by multiple screws.

[0008] Furthermore, in the auxiliary support mechanism, a first hand wheel is provided at the upper ends of the plurality of first screw rods, a thread groove is opened at the lower ends of the plurality of first screw rods, the plurality of thread blocks are respectively screwed into the plurality of thread grooves, and the plurality of metal tips are respectively welded to the lower ends of the plurality of thread blocks.

[0009] Furthermore, the second welding plate, the inclined leg, the second screw, the supporting base plate, the circular metal sheet and the circular rubber sheet are arranged in four equal specifications, the four second welding plates are respectively welded transversely to the lower ends of the outer surfaces of the four square sleeves, the four inclined legs are respectively welded obliquely at the connection between the four second welding plates and the lower ends of the outer surfaces of the four square sleeves, and the four supporting base plates are respectively welded transversely to the lower ends of the four inclined legs.

[0010] Furthermore, four second screw rods are respectively arranged to penetrate the supporting bottom plate, and second hand wheels are welded to the upper ends of the four second screw rods.

[0011] Furthermore, the four circular metal sheets are respectively welded transversely to the lower ends of the four second screws, the four circular rubber sheets are respectively adhered to the lower ends of the four circular metal sheets by epoxy resin glue, and the lower ends of the four circular rubber sheets are all provided with anti-slip patterns.

[0012] Beneficial effects of the present invention: A general aviation low-orbit satellite communication terminal of the present invention, because the present invention adds a first welding plate, a first screw, a threaded block, a metal tip, a second welding plate, an inclined support leg, a second screw, a supporting base plate, a circular metal sheet and a circular rubber sheet, this design enables the device to have a stable supporting function, and there is no need to fix the satellite communication terminal body to the outside, which solves the problem that the original satellite communication terminal is inconvenient to disassemble after installation, and improves the disassembly and assembly efficiency of the present invention.

[0013] Because the present invention adds a square frame plate, a mounting plate, a square sleeve, an electric telescopic rod, a limiting ring, a movable wheel and a connecting angle plate, this design enables the device to have an auxiliary movement function and is easy to use without manual transportation. It solves the problem that the original satellite communication terminal needs to be manually transported and transferred after disassembly, which is relatively inconvenient, and improves the convenience of use of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0015] Figure 1 It is a schematic cross-sectional structure diagram of a general aviation low-orbit satellite communication terminal of the present invention;

[0016] Figure 2 This is a front structural schematic diagram of a general aviation low-orbit satellite communication terminal of the present invention;

[0017] Figure 3 This is a schematic diagram of the rear structure of a general aviation low-orbit satellite communication terminal of the present invention;

[0018] Figure 4 for Figure 1 A magnified schematic diagram of point A;

[0019] In the figure: 1-satellite communication terminal body, 2-satellite communication terminal square support rod, 3-easy to move component, 31-square frame plate, 32-mounting plate, 33-flange nut, 34-flange bolt, 35-square sleeve, 36-electric telescopic rod, 37-limiting ring, 38-moving wheel, 39-connecting angle plate, 391-mounting bolt, 4-auxiliary support mechanism, 41-first welding plate, 42-first screw rod, 43-first hand wheel, 44-thread block, 45-thread groove, 46-metal tip, 47-second welding plate, 48-tilted support leg, 49-second screw rod, 50-second hand wheel, 51-support base plate, 52-circular metal sheet, 53-circular rubber sheet. DETAILED DESCRIPTION

[0020] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further explained below in conjunction with specific implementation methods.

[0021] See also Figure 1-Figure 4The present invention provides a technical solution: a general aviation low-orbit satellite communication terminal, including a satellite communication terminal body 1, a mobile component 3 and an auxiliary support mechanism 4. The satellite communication terminal body 1 is longitudinally mounted with a satellite communication terminal square support rod 2 on the back. The mobile component 3 includes a square frame plate 31, a mounting plate 32, a square sleeve 35, an electric telescopic rod 36, a limit ring 37, a moving wheel 38 and a connecting angle plate 39. The square frame plate 31 is welded in the middle of the annular side of the square support rod 2 of the satellite communication terminal. The mounting plate 32 and the square sleeve 35 are arranged in four equal specifications. The four square sleeves 35 are longitudinally welded to the lower ends of the four mounting plates 32, respectively. A mounting plate 32 is installed around the lower end of the square frame plate 31 at equal angles through multiple flanged nuts 33 and multiple flanged bolts 34. The auxiliary support mechanism 4 includes a first welding plate 41, a first screw 42, a threaded block 44, a metal tip 46, a second welding plate 47, an inclined leg 48, a second screw 49, a support base plate 51, a circular metal plate 52 and a circular rubber plate 53. The first welding plate 41, the first screw 42, the threaded block 44 and the metal tip 46 are arranged in multiples of equal specifications. The multiple first welding plates 41 are respectively welded horizontally to the lower ends of the left and right sides of the four square sleeves 35, and the multiple first screws 42 are respectively arranged through the first welding plates 41.

[0022] In the easy-to-move component 3, four electric telescopic rods 36, limiting rings 37 and moving wheels 38 are provided with equal specifications. The four electric telescopic rods 36 and the four limiting rings 37 are respectively longitudinally fixed inside the four square sleeves 35, and the four limiting rings 37 are respectively fixed on the lower ends of the four electric telescopic rods 36. The four moving wheels 38 are respectively located inside the four square sleeves 35 and are respectively fixed on the lower ends of the four electric telescopic rods 36. A small battery is placed on the rear side of the upper end of the square frame plate 31, and the small battery is bidirectionally electrically connected to the four electric telescopic rods 36 through wires. By adding four limiting rings 37, the four electric telescopic rods 36 are respectively longitudinally fixed inside the four square sleeves 35, which is more stable. The setting of the four moving wheels 38 enables the device as a whole to have a mobile function, which is convenient for the transfer of staff.

[0023] There are multiple connecting angle plates 39 of the same specifications, and the multiple connecting angle plates 39 are fixedly connected to the left and right sides of the four square sleeves 35 by multiple mounting bolts 391, and the multiple connecting angle plates 39 are fixedly connected to the four side surfaces of the square support rod 2 of the satellite communication terminal by multiple screws. Through the added connecting angle plates 39 and multiple mounting bolts 391, the four square sleeves 35 and the four side surfaces of the square support rod 2 of the satellite communication terminal can be indirectly connected together.

[0024] In the auxiliary support mechanism 4, a first hand wheel 43 is provided at the upper end of each of the multiple first screw rods 42, a thread groove 45 is opened at the lower end of each of the multiple first screw rods 42, a plurality of thread blocks 44 are respectively screwed into the plurality of thread grooves 45, and a plurality of metal spikes 46 are respectively welded to the lower ends of the plurality of thread blocks 44. By adding the plurality of metal spikes 46, the plurality of first screw rods 42 can be inserted into the external soil ground when the device is on the external soil ground.

[0025] Four second welding plates 47, inclined legs 48, second screws 49, supporting base plates 51, circular metal sheets 52 and circular rubber sheets 53 are provided with equal specifications. The four second welding plates 47 are respectively welded transversely to the lower ends of the outer surfaces of the four square sleeves 35, the four inclined legs 48 are respectively welded obliquely at the connection between the four second welding plates 47 and the lower ends of the outer surfaces of the four square sleeves 35, and the four supporting base plates 51 are respectively welded transversely to the lower ends of the four inclined legs 48. By adding the second welding plates 47, inclined legs 48, second screws 49, supporting base plates 51, circular metal sheets 52 and circular rubber sheets 53, the device can be more stable when placed on the ground.

[0026] The four second screw rods 49 are respectively arranged to penetrate the supporting bottom plate 51 , and the upper ends of the four second screw rods 49 are welded with second hand wheels 50 . The added second hand wheels 50 facilitate the staff to rotate the four second screw rods 49 .

[0027] The four circular metal sheets 52 are horizontally welded to the lower ends of the four second screws 49, and the four circular rubber sheets 53 are respectively adhered to the lower ends of the four circular metal sheets 52 by epoxy resin glue. The lower ends of the four circular rubber sheets 53 are all provided with anti-slip textures. By adding the four circular metal sheets 52 and the four circular rubber sheets 53, the overall support of the device is more stable when it is placed on the external ground.

[0028] As an embodiment of the present invention: before the satellite communication terminal body 1 needs to be transferred, the square frame plate 31 is welded in the middle of the annular side surface of the square support rod 2 of the satellite communication terminal, and four mounting plates 32 are installed at the lower end of the square frame plate 31 using an external wrench, multiple flange nuts 33 and multiple flange bolts 34. Then, an external wrench is used to install multiple connecting angle plates 39 on the left and right ends of four square sleeves 35 through multiple mounting bolts 391. Then, an external screwdriver and multiple screws are used to fix the rear ends of the multiple connecting angle plates 39 to the four side surfaces of the satellite communication terminal body 1. Then, the setting of the four square sleeves 35 can be completed. Then, the four electric telescopic rods 36 are energized at the same time through a small battery, and the four electric telescopic rods 36 will extend downward, and will drive the four moving wheels 38 to extend downward until the four moving wheels 38 extend downward from the four square sleeves 35, and according to the mutuality of force, the four square sleeves 35, the square frame plate 31, the square support rod 2 of the satellite communication terminal and the satellite communication terminal body 1 are lifted up, and then the device can be pulled to move.

[0029] As an embodiment of the present invention: when the device is moved to the external concrete ground, the four electric telescopic rods 36 are controlled to retract by a small battery, so that when the four moving wheels 38 are completely moved into the four square sleeves 35, the lower ends of the four square sleeves 35 will contact the external concrete ground, and the multiple first hand wheels 43 will be rotated downward, and the multiple first screws 42 will rotate and move downward (at this time, the multiple thread blocks 44 are not installed in the multiple thread grooves 45), until the lower ends of the multiple first screws 42 are against the external concrete ground, the four second hand wheels 50 are rotated downward, and the four second screws 49 will drive the four through the support bottom plate 51. The circular metal sheet 52 and the four circular rubber sheets 53 move downward until the lower ends of the four circular rubber sheets 53 are attached to the external concrete ground, and the placement of the device is completed; if the satellite communication terminal body 1 is moved to the external soil ground, the threaded block 44 is screwed into the multiple threaded grooves 45 in advance, and the lower ends of the four circular rubber sheets 53 are attached to the external soil ground according to the above steps, and the multiple first hand wheels 43 are rotated downward, and the multiple first screws 42 and the multiple metal spikes 46 will rotate and move downward until the multiple metal spikes 46 are completely screwed into the external soil ground, so that the satellite communication terminal body 1 can be stably supported.

[0030] The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention. It is obvious to those skilled in the art that the present invention is not limited to the details of the above exemplary embodiments, and the present invention can be implemented in other specific forms without departing from the spirit or basic features of the present invention. Therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive. The scope of the present invention is limited by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims are included in the present invention.

[0031] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A general aviation low-orbit satellite communication terminal, comprising a satellite communication terminal body (1), a mobile component (3) and an auxiliary support mechanism (4), characterized in that: The satellite communication terminal body (1) is longitudinally mounted with a satellite communication terminal square support rod (2) on the back, and the easy-to-move component (3) comprises a square frame plate (31), a mounting plate (32), a square sleeve (35), an electric telescopic rod (36), a limit ring (37), a moving wheel (38) and a connecting angle plate (39). The square frame plate (31) is welded in the middle of the annular side of the satellite communication terminal square support rod (2). The mounting plate (32) and the square sleeve (35) are arranged in four equal specifications. The four square sleeves (35) are longitudinally welded to the lower ends of the four mounting plates (32) respectively. The four mounting plates (32) are connected by a plurality of flange nuts (33) and a plurality of flange bolts (34). The auxiliary support mechanism (4) is installed around the lower end of the square frame plate (31) at an angle, and comprises a first welding plate (41), a first screw rod (42), a threaded block (44), a metal tip (46), a second welding plate (47), an inclined leg (48), a second screw rod (49), a supporting bottom plate (51), a circular metal plate (52) and a circular rubber plate (53). The first welding plate (41), the first screw rod (42), the threaded block (44) and the metal tip (46) are provided in multiple numbers with equal specifications. The multiple first welding plates (41) are respectively transversely welded to the lower ends of the left and right sides of the four square sleeves (35), and the multiple first screw rods (42) are respectively penetrated through the first welding plates (41); In the easy-to-move component (3), four electric telescopic rods (36), limiting rings (37) and moving wheels (38) are provided with equal specifications. The four electric telescopic rods (36) and the four limiting rings (37) are respectively longitudinally fixed inside four square sleeves (35), and the four limiting rings (37) are respectively fixedly sleeved on the lower ends of the four electric telescopic rods (36). The four moving wheels (38) are respectively located inside the four square sleeves (35) and are respectively fixed on the lower ends of the four electric telescopic rods (36). A small storage battery is placed on the rear side of the upper end of the square frame plate (31), and the small storage battery is bidirectionally electrically connected to the four electric telescopic rods (36) through wires. The connecting angle plates (39) are provided in multiple sizes, and the connecting angle plates (39) are fixedly connected to the left and right sides of the four square sleeves (35) by multiple mounting bolts (391), and the connecting angle plates (39) are fixedly connected to the four side surfaces of the square support rod (2) of the satellite communication terminal by multiple screws.

2. A general aviation low-orbit satellite communication terminal according to claim 1, characterized in that: In the auxiliary support mechanism (4), the upper ends of the plurality of first screw rods (42) are each provided with a first hand wheel (43), the lower ends of the plurality of first screw rods (42) are each provided with a thread groove (45), the plurality of thread blocks (44) are respectively screwed into the plurality of thread grooves (45), and the plurality of metal tips (46) are respectively welded to the lower ends of the plurality of thread blocks (44).

3. A general aviation low-orbit satellite communication terminal according to claim 1, characterized in that: The second welding piece (47), the inclined leg (48), the second screw (49), the supporting base plate (51), the circular metal sheet (52) and the circular rubber sheet (53) are arranged in four equal specifications. The four second welding pieces (47) are respectively welded transversely to the lower ends of the outer surfaces of the four square sleeves (35). The four inclined legs (48) are respectively welded obliquely to the connection between the four second welding pieces (47) and the lower ends of the outer surfaces of the four square sleeves (35). The four supporting base plates (51) are respectively welded transversely to the lower ends of the four inclined legs (48).

4. A general aviation low-orbit satellite communication terminal according to claim 3, characterized in that: The four second screw rods (49) are respectively arranged to penetrate the supporting bottom plate (51), and the upper ends of the four second screw rods (49) are all welded with a second hand wheel (50).

5. A general aviation low-orbit satellite communication terminal according to claim 3, characterized in that: The four circular metal sheets (52) are respectively welded transversely to the lower ends of the four second screw rods (49); the four circular rubber sheets (53) are respectively adhered to the lower ends of the four circular metal sheets (52) by epoxy resin glue; and the lower ends of the four circular rubber sheets (53) are all provided with anti-slip patterns.

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